並列タイトル等Development and Study of LOX Turbopump for LOX/LH2 Rocket Engine
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-588
一般注記The development of a 10 ton thrust liquid oxygen and liquid hydrogen(LOX and LH2)rocket engine is conducted by the National Space Development Agency. The LOX/LH2 engine uses the gas-generator cycle and has dual shaft turbopums with turbines in series. The National Aerospace Laboratory has carried out the development and study of the turbopumps for the engine in co-operation with the National Space Development Agency. The present report descibes the first development and study of the LOX turbopump, which was conducted chiefly by the National Aerospace Laboratory. The LOX turbopump consists of a single stage centrifugal pump with a cavitating inducer and a single-stage two-rotor velocity compounded impulse turbine. The performance of the test turbopump, including the pump pressure rise, the pump and turbine efficiency, turbine power, etc., showed good agreement with the predicted values. The turbopump assembly and most of the components, except the gas seals, also showed good performance through out all the tests. One problem experienced with regard to the gas seals was solved by the modification of the seals. The technical data obtained in this development and study are utilized in order to make the flight type LOX turbopump.
資料番号: NALTR0588000
レポート番号: NAL TR-588
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44842&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ